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and stab trim systems are performing self test once hydraulics are applied. The
horizontal stabilizer system is inoperative through the duration (approximately 20
seconds) of the test. Refer to the EICAS MESSAGES in the spoiler section of flight
controls for the message display.
GX_10_023
CLACKER
CONFIGURATION WARNING
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-28 For Training Purposes Only
Sept 04
Flight Control Invalid Data Displays
ND
STAB
–TRIMS–
NL RUDDER NR
NU
AIL
LWD RWD
FLIGHT CONTROLS
FLAP –––
AIL
ELEV
RUDDER
SLAT –––
AIL
ELEV
GX_10_024
Spoiler Invalid
Flap Invalid
Aileron Position
Indication invalid
Rudder/Position
Indication Invalid
Aileron Surface
Hydraulic Pressure
Not Available
Spoiler Position
Vector
Slat Invalid
Elevator Position
Indication Invalid
Control surface
displays:
• Flaps
• Slats
• Spoilers
Trim displays:
• Aileron
• Rudder
• Stabilizer
INVALID DATA
INVALID DATA
For Training Purposes Only
Sept 04
10-29
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
SLAT/FLAP CONTROL SYSTEM
The slat and flap control system is an integrated electromechanical system which
operates both slats and flaps from a single flight compartment control lever. The slat
and flap control systems are mechanically independent. Each system is comprised of
actuators, linked through a rigid driveline, to a central Power Drive Unit (PDU). Each
PDU incorporates dual electric motor/brake assemblies. The slats and flaps will
continue to operate at half-speed with a single motor operating.
Asymmetry brakes for both slats and flaps are installed to provide driveline braking in
the event of shaft failures. Dual sensors are located at the outboard-most ends of the
driveline. They are used by the control units for system positioning and fault
monitoring. Position sensors are located next to each flap actuator to provide position
feedback to the control units.
The slats are extended first if both slat and flap extension are required. The flaps are
retracted first if both slat and flap retraction is required.
Two Slat/Flap Control Units (SFCUs) control the operation of the slats and flaps.
Electrically there are two independent channels for slats, and two independent
channels for flaps. Each SFCU controls and monitors the slats and flaps independently
of the other unit. Each SFCU controls one slat PDU motor and asymmetry brake, and
one flap PDU motor and asymmetry brake. System control provides protection against
asymmetry and uncommanded movement.
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-30 For Training Purposes Only
Sept 04
SLAT/FLAP System Schematic
SLAT CONTROL SYSTEM
The slat system has four leading edge slat panels with two actuators per slat, connected
to a slats Power Drive Unit (PDU), linked through a rigid driveline (torque tubes/
bearings), and controlled by the slat/flap handle position. The PDU is driven by two
DC motors connected together in a speed sum configuration. Each motor is controlled
by a single channel SFCU. There is a brake on each slat motor that is also controlled
by the SFCU. The PDU provides protection against overload and jam conditions. To
protect against asymmetry, there are dual coil brakes and position sensors, located on
each outboard station, left and right, that interface with both SFCUs.
Anti-icing of the slats is controlled by the ice detection system. Telescopic ducting is
installed between the inboard fixed leading edge and the outboard slats for anti-icing.
Refer to Chapter 3 for additional information on the anti-icing/bleed system.
GX_10_025
SFCU
1
SFCU
2
Driveline SLAT SYSTEM
FLAP SYSTEM
Slat
System
Flap
System
SLAT/FLAP
CONTROL
LEVER
SLAT
6
16
30
0
0
OUT
OUT
OUT
OUT
IN
FLAP
SLAT/
FLAP
1 DC motor per SFCU channel =
2 motors per system
For Training Purposes Only
Sept 04
10-31
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
Slat System Schematic
The slat position (in or out) and surface position is displayed on the FLIGHT
CONTROL synoptic page. Slat indication is also shown on the EICAS PAGE.
GX_10_026
SFCU
1
SFCU
2
SLAT/FLAP
CONTROL
LEVER
Driveline
　
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